Combustor dilution hole cooling

Abstract

Aspects of the disclosure are directed to a method for forming a cooling circuit in at least one of a combustor panel or liner wall of an aircraft engine. The method includes producing a substrate with the cooling circuit formed in the substrate, where the cooling circuit is located in proximity to an aperture associated with the at least one of a panel or liner wall.

What is claimed is: 
     
         1 . A method for forming a cooling circuit in at least one of a combustor panel or liner wall of an aircraft engine, comprising:
 producing a substrate with the cooling circuit formed in the substrate,   wherein the cooling circuit is located in proximity to an aperture associated with the at least one of a panel or liner wall.   
     
     
         2 . The method of  claim 1 , wherein the substrate and the cooling circuit in said substrate are produced via one of the following:
 casting with an external surface profile to create the cooling circuit;   casting with at least one external or surface core to create the cooling circuit;   casting with a machined surface to create the cooling circuit;   forging or sheet metal with a machined or formed cooling circuit;   using a ceramic or a composite with a machined or fabricated cooling circuit; or   using an additive manufacturing technique.   
     
     
         3 . The method of  claim 1 , further comprising:
 inserting a material into the cooling circuit as at least one of an inlay or filler.   
     
     
         4 . The method of  claim 3 , wherein the material comprises at least one of:
 at least one of a core or refractory material; or   at least one of a maskant or shadow material.   
     
     
         5 . The method of  claim 3 , further comprising:
 at least one of coating or plating the cooling circuit on a surface of the substrate to create a wall.   
     
     
         6 . The method of  claim 5 , wherein the surface corresponds to an external wall of the substrate configured to face a flowpath. 
     
     
         7 . The method of  claim 5 , wherein the surface corresponds to an inner wall of the substrate that is configured to be opposite a flowpath. 
     
     
         8 . The method of  claim 5 , wherein the at least one of coating or plating comprises an application of a bond coat. 
     
     
         9 . The method of  claim 5 , further comprising:
 removing the insert material.   
     
     
         10 . The method of  claim 9 , wherein the insert material is removed using at least one of:
 etching;   application of a chemical; or   a thermal technique.   
     
     
         11 . The method of  claim 9 , further comprising:
 applying part post-processing.   
     
     
         12 . The method of  claim 11 , wherein the part post-processing comprises application of at least one of:
 a thermal barrier coating;   an environmental barrier coating;   a corrosion coating;   a laser;   grind machining; or   electrodischarge machining.   
     
     
         13 . A combustor panel or a liner wall of an aircraft engine, comprising:
 a substrate; and   a cooling circuit formed in the substrate in proximity to an aperture of the combustor panel or liner wall.   
     
     
         14 . The combustor panel or liner wall of  claim 13 , wherein the cooling circuit is formed based on a removal of an insert material. 
     
     
         15 . The combustor panel or liner wall of  claim 13 , wherein the cooling circuit is formed in the substrate on a side of the substrate that is configured to face the engine. 
     
     
         16 . The combustor panel or liner wall of  claim 13 , wherein the cooling circuit is formed in the substrate on a side of the substrate that is configured to oppose the engine. 
     
     
         17 . The combustor panel or liner wall of  claim 13 , further comprising:
 a metal coating or plating coupled to a surface of the substrate.   
     
     
         18 . The combustor panel or liner wall of  claim 13 , wherein the aperture comprises at least one of:
 a first hole that is configured to supply air to a combustion of a fuel-air mixture,   a second hole configured to accommodate at least one of:
 an ignitor, 
 a probe, or 
 a sensor, or 
   a third hole in a bulkhead.   
     
     
         19 . The combustor panel or liner wall of  claim 18 , wherein the first hole comprises at least one of a dilution hole, a trim hole, or a feed hole. 
     
     
         20 . The combustor panel or liner wall of  claim 13 , wherein the cooling circuit is at least one of:
 adjacent to a grommet,   integral to the grommet, or   partially incorporated in the grommet.